CN204916167U - Many rotor unmanned aerial vehicle carbon pipe damping shock attenuation undercarriage - Google Patents
Many rotor unmanned aerial vehicle carbon pipe damping shock attenuation undercarriage Download PDFInfo
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- CN204916167U CN204916167U CN201520533005.0U CN201520533005U CN204916167U CN 204916167 U CN204916167 U CN 204916167U CN 201520533005 U CN201520533005 U CN 201520533005U CN 204916167 U CN204916167 U CN 204916167U
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- unmanned aerial
- shock absorber
- damping shock
- aerial vehicle
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Abstract
The utility model belongs to the technical field of the aircraft, especially many rotor unmanned aerial vehicle field relates to a many rotor unmanned aerial vehicle carbon pipe damping shock attenuation undercarriage, aims at providing one kind and optimizes many rotor unmanned aerial vehicle descending action through pure mechanical system, revises unusual descending state, and protection complete machine and inside data security reduce to fall the undercarriage of the fried quick -witted risk of machine. The utility model discloses a pack up mechanism, axle head, damping bumper shock absorber, cover end, rubber protection pad, axle head and cover end between install the damping bumper shock absorber, the damping bumper shock absorber install at set end insidely, cover bottom of a matter portion be fixed with the rubber protection pad, the rubber protection pad is direct with the installation of cover end with dismantle with the interference fit mode, the damping bumper shock absorber adopt the pneumatic bumper. The utility model discloses the kinergety in the twinkling of an eye that produces in the time of can absorbing unmanned aerial vehicle and descend realizes the soft landing of descending each time, extension complete machine life.
Description
Technical field
The utility model belongs to vehicle technology field; particularly many rotor wing unmanned aerial vehicles field; relate to a kind of many rotor wing unmanned aerial vehicles carbon pipe damping shock absorption alighting gear; aim to provide one and optimize many rotor wing unmanned aerial vehicles dropping action by pure mechanical system; revise abnormal state of landing; protection complete machine and internal data safety, reduce the alighting gear falling machine aircraft bombing risk.The instant movement energy that the utility model produces when can absorb unmanned plane landing, realizes the soft landing of landing each time, extends complete machine service life.
Background technology
Many rotor wing unmanned aerial vehicles have cost low, easy to operate, there is high degree of flexibility and can the feature such as hedgehopping, its photographic equipment carried can be utilized to carry out picture photographing, obtain image data, and obtained image data is sent back ground.Many rotor wing unmanned aerial vehicles be widely used at present take photo by plane, power-line patrolling, aerial reconnaissance, simulated flight, the field such as subsidy unmanned plane, in order to monitor the observation etc. of evidence obtaining and specific position, the transmission implementing live video picture can be realized, carrying out decision-making and judgement for director, is a kind of important tool of obtaining information.In addition, many rotor wing unmanned aerial vehicles of easy structure also receive at toy art and like widely.
Guarantee when alighting gear is unmanned plane landing, the shock-proof effect of alighting gear also has influence on vibration amplitude when unmanned plane lands, particularly under the condition that neophyty operation is unskilled and special assignment terrain environment operation easier is high, shake excessive will formation and fall machine aircraft bombing, not only affect completing smoothly of task, also result in high economic loss.At present; alighting gear on market, mainly through adding the mode absorbing vibration of cushion rubber, all can not be pulled off a soft landing, therefore; the utility model has designed and developed out a kind of alighting gear that can overcome above-mentioned defect, seems particularly important in raising task efficiency and protection unmanned plane secure context.
Utility model content
The technical problems to be solved in the utility model is: provide a kind of and optimize many rotor wing unmanned aerial vehicles dropping action by pure mechanical system, revises abnormal state of landing, protection complete machine and internal data safety, reduces the alighting gear falling machine aircraft bombing risk.
The technical scheme that the utility model is taked for the technical matters existed in solution known technology is:
A kind of many rotor wing unmanned aerial vehicles carbon pipe damping shock absorption alighting gear, comprises stow mechanism, axle head, damping shock absorber, cover end, rubber protection pad, is provided with damping shock absorber between described axle head and cover end; It is inner that described damping shock absorber is arranged on cover end; Described cover bottom portion is fixed with rubber protection pad, and rubber protection pad directly holds Assembly &Disassembly with cover with interference fit.
As preferably, the utility model additionally uses following technical scheme:
Further: described damping shock absorber adopts pneumatic bumper, and comprise seal ring, piston rod, piston, rebound valve, shrinking valve, cylinder framework, described seal ring, piston rod, piston connect successively; Described rebound valve, shrinking valve are arranged on piston.
The advantage that the utility model has and good effect are: in the utility model, optimize many rotor wing unmanned aerial vehicles dropping action by pure mechanical system, revise abnormal state of landing, protection complete machine and internal data safety, reduce the alighting gear falling machine aircraft bombing risk.The instant movement energy that the utility model produces when can absorb unmanned plane landing, realizes the soft landing of landing each time, extends complete machine service life.Therefore, it is possible to strengthen the structural strength of aircraft frame well; The impact resistance of aircraft is greatly improved.
Accompanying drawing explanation
Fig. 1 is front view of the present utility model;
Fig. 2 is lateral plan of the present utility model;
Fig. 3 is birds-eye view of the present utility model;
Fig. 4 is local structure schematic diagram of the present utility model, is mainly used in the structure showing damping shock absorber.
Wherein: 1, stow mechanism; 2, axle head; 3, seal ring; 4, piston rod; 5, piston; 6, rebound valve; 7, shrinking valve; 8, cylinder framework; 9, cover end; 10, rubber protection pad.
Detailed description of the invention
For utility model content of the present utility model, Characteristic can be understood further, hereby exemplify following examples, and coordinate accompanying drawing to be described in detail as follows:
Refer to Fig. 1 to Fig. 4: a kind of many rotor wing unmanned aerial vehicles carbon pipe damping shock absorption alighting gear, comprises stow mechanism, axle head, damping shock absorber, cover end, rubber protection pad, between described axle head and cover end, damping shock absorber is installed; It is inner that described damping shock absorber is arranged on cover end; Described cover bottom portion is fixed with rubber protection pad, and rubber protection pad directly holds Assembly &Disassembly with cover with interference fit.
As preferably, described damping shock absorber adopts pneumatic bumper, and comprise seal ring, piston rod, piston, rebound valve, shrinking valve, cylinder framework, described seal ring, piston rod, piston connect successively; Described rebound valve, shrinking valve are arranged on piston.
Above embodiment of the present utility model has been described in detail, but described content being only preferred embodiment of the present utility model, can not being considered to for limiting practical range of the present utility model.All equalizations done according to the utility model application range change and improve, and all should still belong within patent covering scope of the present utility model.
Claims (2)
1. the carbon of rotor wing unmanned aerial vehicle more than a pipe damping shock absorption alighting gear, comprises stow mechanism, axle head, damping shock absorber, cover end, rubber protection pad, it is characterized in that: be provided with damping shock absorber between described axle head and cover end; It is inner that described damping shock absorber is arranged on cover end; Described cover bottom portion is fixed with rubber protection pad, and rubber protection pad directly holds Assembly &Disassembly with cover with interference fit.
2. many rotor wing unmanned aerial vehicles carbon pipe damping shock absorption alighting gear according to claim 1, it is characterized in that: described damping shock absorber adopts pneumatic bumper, comprise seal ring, piston rod, piston, rebound valve, shrinking valve, cylinder framework, described seal ring, piston rod, piston connect successively; Described rebound valve, shrinking valve are arranged on piston.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520533005.0U CN204916167U (en) | 2015-07-21 | 2015-07-21 | Many rotor unmanned aerial vehicle carbon pipe damping shock attenuation undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520533005.0U CN204916167U (en) | 2015-07-21 | 2015-07-21 | Many rotor unmanned aerial vehicle carbon pipe damping shock attenuation undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204916167U true CN204916167U (en) | 2015-12-30 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520533005.0U Expired - Fee Related CN204916167U (en) | 2015-07-21 | 2015-07-21 | Many rotor unmanned aerial vehicle carbon pipe damping shock attenuation undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204916167U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005378A (en) * | 2016-06-30 | 2016-10-12 | 张春生 | Undercarriage for shipborne unmanned aerial vehicle |
| CN106005375A (en) * | 2016-06-03 | 2016-10-12 | 全蕊 | Unmanned gyroplane landing gear and unmanned gyroplane |
| CN106828889A (en) * | 2017-01-19 | 2017-06-13 | 福州大学 | Unmanned plane protection device and its method of work |
| CN111824365A (en) * | 2020-07-15 | 2020-10-27 | 中船重工（海南）飞船发展有限公司 | Ground effect wing ship landing wheel device |
-
2015
- 2015-07-21 CN CN201520533005.0U patent/CN204916167U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005375A (en) * | 2016-06-03 | 2016-10-12 | 全蕊 | Unmanned gyroplane landing gear and unmanned gyroplane |
| CN106005378A (en) * | 2016-06-30 | 2016-10-12 | 张春生 | Undercarriage for shipborne unmanned aerial vehicle |
| CN106828889A (en) * | 2017-01-19 | 2017-06-13 | 福州大学 | Unmanned plane protection device and its method of work |
| CN111824365A (en) * | 2020-07-15 | 2020-10-27 | 中船重工（海南）飞船发展有限公司 | Ground effect wing ship landing wheel device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160912 Address after: 300000 Tianjin city Hexi District chentangzhuang Dongting Road No. 20 Chen Tong Technology Business District Service Center 302-1 Patentee after: Tianjin City, Xiao Qi Yi cloud Technology Co. Ltd. Address before: 300110, Tianjin, Nankai District Nankai three road and the Yangtze River Road junction, Financial Street center, block B, 2010 Patentee before: TIANJIN XIAOQI TECHNOLOGY DEVELOPMENT CO., LTD. |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20170526 Address after: 300110, Tianjin, Nankai District Nankai three road and the Yangtze River Road junction, Financial Street center, block B, 2010 Patentee after: TIANJIN XIAOQI TECHNOLOGY DEVELOPMENT CO., LTD. Address before: 300000 Tianjin city Hexi District chentangzhuang Dongting Road No. 20 Chen Tong Technology Business District Service Center 302-1 Patentee before: Tianjin City, Xiao Qi Yi cloud Technology Co. Ltd. |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151230 Termination date: 20180721 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |